• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.3
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• pp.229-236
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• 2014

In this paper, the guidance laws and controllers for the gliding guided artillery munition is studied. The gliding guided artillery munition has wings for gliding to increase a range; therefore previous guidance laws and controllers for the guided munition could not be applied. Concepts of vector field guidance and proportional navigation guidance are applied for mid-term and terminal guidance, respectively. The gliding guided artillery munition is operated within wide altitude and speed areas; therefore, the controllers are designed for each area, and gain-scheduling and the linear interpolation technique is applied to compute the appropriate gains.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.3
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• pp.221-228
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• 2014

In this paper, the operational concept and the navigation algorithms for the gliding guided artillery munition are studied. The gliding guided artillery munition has wings for gliding; therefore spin of the munition should be eliminated. The previous navigation algorithms assumed a spinning munition with constant angular velocity; hence, they cannot be applied for the gliding munition. Moreover, lateral stability becomes worse due to decrease of angular momentum. Therefore, side force should be controlled to improve the stability, and the munition should maneuver, then the previous navigation algorithms for typical fixed-wing aircraft cannot be applied. In this paper, we apply the previous navigation algorithms for the spinning munition. Spin is eliminated and wings are deployed based on the estimation results, and the advanced navigation algorithm for the non-spinning munition is introduced.

• Journal of Industrial Technology
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• v.35
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• pp.9-13
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• 2015

In this paper, a new excitation scheme is developed to increase the output torque of the sensorless BLDC(Brushless DC) motor(BLDCM), which drives fins to control the flight attitude of a guided artillery munition. The proposed scheme is based on a 12-step excitation strategy combining two-phase and three-phase excitations. The proposed 12-step excitation scheme can produce more torque than a typical 6-step scheme for the start-up and synchronous operation in the sensorless BLDCM drive. The simulation and experimental results on the sensorless BLDCM drive system to control the fin were verified the validity of the proposed scheme.

• The Transactions of the Korean Institute of Power Electronics
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• v.20 no.6
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• pp.580-586
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• 2015

A brushless DC (BLDC) motor control system for four-axis driving fins to control the flight attitude of a guided artillery munition is developed in this study. This system adopts a simple sensorless control scheme without a Hall sensor. A 12-step driving sensorless BLDC motor scheme is used to improve the output torque. This system has many restrictive problems that hinder the verification of a real system. For example, this has cost and environmental limitations. Therefore, this study develops HILS to verify a four-axis driving fin control system and verifies the position control system hardware by HILS operation.

• The Transactions of the Korean Institute of Power Electronics
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• v.19 no.4
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• pp.342-348
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• 2014

In this paper, a BLDC(Brushless DC) motor control system for driving fins to control the flight attitude of the guided artillery munition is developed. This system adopts a sensorless control scheme without any position sensor such as a Hall sensor fragile at high altitudes. The sensorless control of the BLDC motor is achieved by using commutation signals obtained from the measured pole voltages. The position control of the fin is also performed by using of the estimated speed from the commutation signals. The experimental results on the actual fin drive system demonstrated that the developed sensorless control algorithm can give an excellent position control performance.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.9
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• pp.681-689
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• 2020

This paper presents methods and results of both flight test examining roll angle estimation performance of slowly rolling munition forced to spin in the air, and fabricating a replica of guided munition. Guided munition was deployed from multi rotor type UAV mother ship whose altitude and velocity was conveyed to it as initial state. Flight test scenario is composed of a sequence of munition drop(deployment), munition spin, roll angle estimation and stabilization. Munition was deployed from mother ship at around 200m high with horizontal velocity of 15m/s, and was made spun using internal reaction wheel. Performance analysis on roll angle estimation is provided in comparison with commercial aerospace graded GPS/INS. Moreover, several mechanisms that rotates munition using reaction wheel, and actual product that realizes one of them are introduced.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.9
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• pp.752-759
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• 2018

This paper presents methods and results of nonlinear simulations for a guided munition for verifying stability at slow spin. The munition is launched by an artillery and it deploys the rear fins to reduce its spin. While the spin speed command is set to 1 rps and 3 rps, wind gusts of 3m/s, 7m/s, 10m/s, and 15m/s in amplitude, and 26 different directions were generated as disturbance for each simulation run. Whereas the munition with the spin speed of 3 rps didn't flip, that with 1-rps spin flipped under some gusts. However, the gusts which increase airspeed in the flight direction didn't introduce harmful effect. Most importantly, all the flips of the munition was observed near the end of the simulation where the munition is going down. No problem was observed near the summit of trajectory.

• Proceedings of the KIPE Conference
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• 2015.07a
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• pp.133-134
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• 2015

본 논문에서는 유도형 활공 탄약의 방향과 자세 제어를 위한 4축 조종 날개의 위치 제어용 Sensorless BLDC 전동기 구동 시스템을 개발하였다. HILS(Hardware in the loop system)를 이용하여 유도형 탄약의 발사 조건과 비행 환경을 시뮬레이션하면서 비행 시 발생하는 공력 부하를 기구부로 재현하였고 이러한 조건하에서 4축 조종 날개의 위치 제어 특성을 확인함으로써 개발된 구동 시스템의 성능을 검증하였다.

• Journal of the Korea Institute of Military Science and Technology
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• v.11 no.6
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• pp.21-29
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• 2008

Korean army currently considers the development of the advanced MLRS(Multiple Launcher Rocket System) as a new alternative, which responses on the renovation of the artillery and future battle field environment. Therefore, This study suggests that the development methods of MLRS based on the analysis of the future battle field environment, world wide development trends of the MLRS and operation states of the domestic MLRS. According to this study, the development methods of new generation MLRS should be included a 230/130mm combined launcher competible with conventional 227mm on the vehicle, advanced FCS(Fire Control System), GPS/INS integration navigation system, Pod of ammunitiom, ammunition carrring vehicle and guided rocket munitions, etc.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.5
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• pp.373-381
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• 2021

This paper details the result of flight experiment that examines performance of roll angle estimation algorithm of slowly rolling munition taking time delay of measurement into account when measurement comes in delayed fashion. As the measurement is passed through low pass filter for numerical stabilization and de-noising purpose which induces time delay, we design augmented state Kalman filter that incorporates distribution models of stochastic delay over time. Flight experiment was conducted to verify the algorithm at around 250m high AGL(Above Ground Level) conveying velocity of 28m/s from fixed-wing mother plane to the munition. Munition was made spun with respect to its roll axis using internal reaction wheel afterward. Numerical comparison of proposing method's roll estimation performance with that of commercial aerospace graded GPS/INS shows that proposed filter design can effectively compensate time delay of measurement.